UA77018C2 - Aircraft - Google Patents

Abstract

An aircraft (10), in particular a trainer aircraft with improved aerodynamic perfomance, having a configuration able to keep a directional stability and a very good aerodynamic behaviour even at very high angles of attack, where, traditional configurations prove themselves inefficient. In particular, this configuration foresees a forebody (52) with variable section, optimized for high angle of attack flights, a LEX vortex control device (72) at least one diverterless air intake (46), and a wing profile (18, 20) optimized in order to reduce the buffer effects typical of low aspect ratio wings with thin profile and variable camber. The aircraft (10) presents, finally, staggered tails (44 and 38), to optimize the aerodynamic performance.

Description

attack (the angle between the aircraft and the direction of the approach to the wings with its nose edge blocking the air flow at any moment). rear ribs of the wings to support the side stabi-

It is easy to understand that in such flight conditions laziness. for reliable provision of spatial orientation. It is this design that allows the creation of an aircraft that should be very stable and easily similar to a pilot-controlled training aircraft. flight technical and operational characteristics

This stability is provided and used by the artists. or special automatic equipment capable This layout includes a twin-engine form to create the forces and moments needed to counteract the performance of the aircraft and is distinguished by the presence of a number of undesirable situations in flight. very specific structural elements.

While the stability of the aircraft along the pitch axis Combined with a two-seater cockpit (tandem) with can be controlled by optimizing the stock of static interconnected nose stability controls and the amplitude doubling time, the side part, which has a substantially circular variable cross-section, instability (axially roll and yaw) with small relative elongation and large angles of attack can be difficult to control - optimized for flights at large angles of attack. even with the use of modern control systems, a radar for flight guidance can be easily built into this part. combat aircraft.

Therefore, there is a need for the maximum The shape and dimensions of the nose part are optimized to increase the lateral stability of the aircraft at large - to reduce the vortex effect at aerodynamic angles of attack to ensure the controllability and characteristics of the aircraft at medium and high angles of maneuverability of the aircraft, as well as to avoid loss of attack. The mentioned characteristics allow changes in stability and entry into the corkscrew. to sew longitudinal asymmetry at large angles of attack

Earlier, especially recently, there were attempts to modify the aerodynamic shape of the cross-section, typical for the nose part of a round or ellipse. fuselage and other parts of the aircraft. So far, these attempts have not given positive results. unique in that it is able to fit into the system

Therefore, within the framework of the above-mentioned requirements, one subject capable of minimizing the effects of buffeting, characteristic of the problems of the invention, is the solution of the above-mentioned pro-tern for wings with a small relative elongation and blem and, in particular, the problem related to the stem-thin profile of variable curvature. The aerodynamic scheme also includes a device with characteristics capable of optimizing the behavior for managing vortices on the inflow of the wing over the plane, especially during flight at large angles to the wing, the dimensions of which ensure attack. metric separation of these vortices on medium and high

Another task of the invention is to offer good angles of attack, since the symmetrical separation of the layout of the aircraft with improved aerodynamic vortices contributes to lateral stability and controllability, which can reduce the impact of the aircraft at medium and large angles of attack. fitting, characteristic of wings with a small relative According to the invention, the training-training li- lengthening, thin profile and variable curvature has at least one air intake for it. engine capable of providing flight and technical

A further task of the invention is to create a li- characteristics and a proper hydrodynamic relationship with improved aerodynamic characteristics with the engine, while such an aircraft does not have noses, which would ensure successful avoidance requires the embedding of a typical deflector on the lateral stability vertices and the negative impact of the lip of the air intake, combined with the inflow of gases from the engine near the wing fuselage wall. and the horizontal tail on the front. Moving back the horizontal tail drag, stability and longitudinal controllability of the wing allows to reduce the aerodynamic front of the aircraft. resistance created by the tail part

Another task of the invention is to create a fuselage, as well as to optimize the behavior of the aircraft with improved aerodynamic characteristics in corkscrew conditions and to improve the aerodynamic tics, capable of ensuring exit from the corkscrew. . large angles of attack. The remaining tasks and advantages of the proposed com-

The task is solved by the aircraft, the novelties of the aircraft will be clear from the further description, which includes the fuselage equipped with wings from the nozzle of the invention and the drawings, where Fig. 1 shows a part of the variable cross section, the proposed layout of the aircraft, in particular the training at least one air intake, as well as the tail of a training aircraft, side view; Fig. 2 shows a horizontal and vertical wing, the proposed layout of the aircraft, in particular the device, according to the invention, equipped with a training aircraft device, top view; in Fig. 3 - for control of vortices on the inflow of the wing on the proposed layout of the aircraft, in particular the training rib, designed to provide a training aircraft, view from below; in Fig. 4 - pro-symmetric detachment of vortices, generated by the noted layout of the aircraft, in particular, by the induced inflow of the wing at medium and large angles of the training aircraft, front view; in Fig. 5 - attacks, while the specified device interacts with the proposed layout of the aircraft, in particular the training tail, in which the vertical and training aircraft, rear view; in Fig. b - cross-section of the horizontal tail feathers shifted relative to the MI-MI line in Fig. 2; in Fig. 7 - a partial longitudinal cross-section of the nose of the fuselage of the aircraft in such a way that the keel is attached; on Fig.8

- section along the MPI-MII line Fig. 7; Fig. 9 is a cross-section of a device for controlling vortices on the inflow of line IX-IIX of Fig. 7; in Fig. 10 - a cross-section along the XX-xX line of the wing, and the tolerances can be determined according to

Fig. 7; in Fig. 11 - section along line XI-XI of Fig. 7; on the bearing between the area of influence of the wing and the height

Fig. 12 - section along the line XII-XI! Fig. 7; in Fig. 13 - the device for controlling the swirl on the inflow of cuts along the line KhPI-KHIII Fig. 7; Fig. 14 is a wing section. The value of this ratio is equal to the line KM-KM Fig. 7; in Fig. 15 - a section along the line ХУ- 2.35 m, and the range of tolerances is from 410095 to

XM Fig. 7; in Fig. 16 - section along the line HMI-HMI Fig. 7; -5095 from the specified value.

Fig. 17 - section along the line KhMII-KHMI! Fig. 7; in Fig. 18 - The shape of the nose part 52 of the fuselage of the aircraft 10 is an element of the layout of the aircraft in axonometry in the collapsing - and its dimensions are optimized to an even greater extent for a large scale. reducing the effect of vorticity on it on the aerodynamic

In these aircraft drawings, in particular, the training characteristics of the aircraft 10 when flying on a training aircraft, which has a layout with medium and large angles of attack, while the mentioned improved aerodynamic quality, the general characteristics are provided, which also allow to reduce the course notation 10. asymmetry at large angles of attack, typical for

The aircraft 10 includes a fuselage 12 with an upper 14 and a nose part of a circular or elliptical cross-section. according to the invention, the nose part 52 of the fuse- on the fuselage two wings, i.e. the right 18 and left 20 of the aircraft bed 10 is characterized by the sequence of the wing, respectively. The right wing 18 has an end 22, and cross-sections of different geometries, starting from the toe 74 on the left - the end 24. of the nose part of the fuselage to its edge, which merges

The plane 10 is also equipped with a rudder 34, connected to the tip of the wing. installed on the keel 38, and the horizontal tail A preferred, but not limiting, version of the feathering 44 with the right 26 and left 28 stabilizer- geometric shape and sequence of sections between us with limbs 30 and 32, respectively. nose 74 of the nose part of the fuselage and the

In the best, but not limiting form, the expression relating to its section 76 (located in the invention, as already mentioned above, approximately at the beginning of the two-seater cabin 54), is a simple two-engine design and corresponding the variant, which is illustrated by the sequence of the foam, is equipped with two air intakes 48 and cuts, presented in Fig. 8-17, from which it can be seen how the nozzles 60 of the engines. a sequential transition from approx

In the front zone 52 of the fuselage, in which for the combat-circular cross-section of the nose part of the fuselage version of the aircraft can be built- (Fig. 8-11) to the ovalized cross-section (Fig. 12-17). equipped radar, the cabin 54 for two pilots is located From the figures of the drawings, you can see lots 3 with the corresponding equipment, the displacement of the nose part 52 of the fuselage along the windshield 62 is protected. It can also be provided along the longitudinal axis K, from the nose 74 to the base section, a hose 58 for refueling the plane 10 in the air. shown in Fig.17. In particular, according to the majority

Each of the wings 18, 20 of the aircraft 10 (Figs. 2 and 3) according to the embodiment of the invention, the ratio is equipped with aileron 56 and a take-off and landing gear of length I! nose part 52 of the fuselage, slotted flap 64, mounted in the rear starting from the toe 74 to the section along the line ХМІІІ- rib 70 of the wing 18, 20, as well as other devices of the ХМІІ, and the average ratio between the value - to optimize the curvature of the wing profile (hanging axes A and B of the cross-section presented in Fig. 17, front rib) 66, mounted in the front is 1.873 with tolerances 510905. rib 68 of the wing. Such a profile is formed in accordance with the structural features and their influence on relations to the special geometry based on the in-flight conditions determined by the combination of the mentioned agrodynamics specified in this description. them above parameters (taking into account tolerances,

In particular, according to the invention, to obtain, if they are) and the sequence of cross-sections of the nose part- high aerodynamic quality and stability of the 52 fuselage from the toe 74 of the fuselage of the aircraft flight, the technical characteristics of the aircraft 10 have 10 to the basic cross-section shown in Fig. 17. to be like that Fig. 18 shows in more detail the air

First of all, the aerodynamics of the aircraft is characterized by the intake 46 of the engine, which is also . copes with the presence of the device 72 (Fig. 1) for controlling the influence on the flight technical characteristics of the aircraft 10, vortices on the inflow of the wing on the nose, first of all, which concerns the gas-dynamic interaction during flights at medium and high angles of mode with a corresponding jet engine . attacks The inflow of the wing with a Gothic shape and the air intake 46 has a leading edge varying up to 6.495 of the total area of the wing (according to the radius optimized in the lower part for the invention) provides the possibility of creating a reduction of the distortion of the air flow at the entrance of the lift force at flights on large engines at large angles of attack and in the lateral part at angles of attack, and the design of the wing inflow is precisely designed to reduce the frontal drag caused by installing at its end a channel of air at near-sonic speeds. of a device for controlling vortices on the inflow of the wing. In particular, the average radius of 76A of the leading edge, which ensures symmetrical separation of vortices at the inner lip of the air intake, is 7 mm in flights at large angles of attack during lateral downsliding and prevents the loss of lateral stable lips, equal to 17.5 mm, and the average cent. the radius of the outer lip is 80, equal to 14 mm. IN

The dimensions of the device 72 for managing vortices, as a result of this, the area of grabbing of the air intake on the inflow of the wing depends on the frontal size is about 0.322m2, the area of its throat of the inflow of the wing, in any case, is about 0.257m", and the frontal area of the engine is about - the greater the inflow of the wing, the greater the angle 0.273m:2 (these values refer to one story

triple intake). compared to standard fenders first of all

The air intake 46 does not have a deflector in the upper part of the front edge of the wing on each side, and it is combined (Fig. b), which, as is known from the prior art, with the inflow of the wing, which is due to a special small round shape , and now received a triangular shape to optimize the position of the brake point of the wing, and the wing inflow actually performs a functional flow in the presence of the leading edge 68 and the screen at large angles of attack. "hanging of the front rib" 66, deflected

The air intake can be equipped with two at medium angles of attack. additional flaps (not shown), the location - As can be seen from Fig. b, which shows a section of them on the upper part of the connection between the wing 18, along the line MI-MI of Fig. 2 on an enlarged scale, each and the fuselage 12, which are opened under the action, the wing has a profile of variable curvature both along the pre-stressed springs mounted in the front rib 66 ("the deflectable front hinge of the flaps, when the pressure in the air intake channel is the rib"), and along the rear rib 70, near ka becomes lower than the pressure at the specified connections between ailerons 56. These ailerons are used only by the wing and fuselage. at near-sonic modes to reduce curvature

The purpose of these flaps is to reduce (in their wing profile to reduce the compressibility effect. in its open position) the local angles of attack. air consumption - 0.36890 with tolerances from 0.595 to 0.295 from the nominal value through the air intake of 46. value, and according to the decision at the general

One of the properties of the aircraft 10, which will ensure the wingspan, for which the elongation of the front one hears its high flight technical characteristics, the rib along the chord is applicable, compared to the standard stability and aerodynamic quality, is the displacement by dart solutions, is equal to 8.295 with tolerances of the forward vertical tail feathers 38 from 41095 to 595 from the nominal value. relative to the horizontal tail 44. Aircraft 10 is also distinguished by the design of the fu

This makes it possible to reduce the frontal drag, which creates an airfoil 12, in the rear part 16 of which is mounted in the rear part of the fuselage, as a result of which the engine nozzles and which has a tail part 90 ensure the optimization of the behavior of the aircraft 10 in (Fig. 3). Thus, the area near the nozzles of the engines under conditions of a corkscrew and, in addition, it is improved, has a more optimal design, at least the aerodynamic quality when flying at large allows to reduce the negative impact on the frontal angles of attack. resistance, as well as on longitudinal stability and steering

The trapezoidal vertical tail, which creates air flows to the engines, is connected to the wings and includes a rudder near the side wall 12 of the fuselage and gas flows in the direction 34. This means that the front edge 36 of the engines near the horizontal tail rudder (Fig. 1) covers the rear ribs 70 of the wings 18, 20, tail 44. which helps the aircraft exit the corkscrew and optimizes the Aircraft 10 also has a three-wheel chassis, the behavior of the aircraft 10 at large angles of attack. which includes bow and main supports. Nasal op-

The horizontal tail of the trapper includes a support rack, four doors that are of a ceidal shape that control two independent front-close compartments, as well as a cleaning mechanism that provides a symmetrical or asymmetrical landing gear in the rear direction. deviation of the rudders. The horizontal tail main support has a landing gear cleaning mechanism equipped with a hinged axle 86 (Fig. 2), which in the forward direction to create cargo space is deflected to the right and left by approximately 7.57 inside the fuselage. from the transverse axis 88 to optimize the articulated According to the invention, the aircraft 10 has a system of moment and moment of inertia. automatic flight control ("electrodis-

They are located with displacement in the longitudinal direction") with a digital quadruplex line horizontal and vertical feathering redundancy, which allows to optimize the flight- can also be characterized by tolerances on technical characteristics. This system ensures the ratio of the distance C (Fig. 1) between the ends of the chords flight safety , automatically limiting the field-root parts of the keel and horizontal tail modes, which could create discomfort 44, to the shoulder of the tail, for pilots or lead to a loss of controllability, which is equal to 4181mm. It follows that this from- (" non-burdensome piloting"). bearing is 1932/4181-0.462 with tolerance From the above characteristics of the layout of 1096. an aircraft with improved aerodynamic characteristics

Therefore, the wing profile is modified and optical scientists, which is the subject of the invention, are completely rhomized compared to the wing of a conventional school-understood advantages of such a layout. of a training aircraft, which provides a reduction. It is also clear that when using the invention, the effect of buffeting, taking into account the low ratio, other extensions of the wing, its thin profile and changes can be made to the layout of the aircraft without going beyond the scope of the patent. In addition, variable curvature. it is clear that during the implementation of the invention can

According to the invention, the wing 18, 20, on the contrary, should be used other materials, shapes and sizes trapezoidal shape and the average relative sub-elements of the aircraft in accordance with the specific use of the AK-4, and is also characterized by the presence of requirements, and some elements can be replaced in- toothed protrusion 5 (fig. 2) at the point corresponding to these elements, which have the same technical characteristics 67,595 of the full span of the wing. This modification of characteristics.

in and 5 your ni tv ne Mi shiv che

Esh au shi SHE She KE sh-- t B-- drink RO SD I fun i y «a shlK

Oh, teach her She is more than she is she is a ko ra that i rat N t h i N o. AND

E 1 and c. mu SHI kv y in B , / ee nk 58 and EV y i. m Shi "bat. t. Zk ki as and in Y them and - and and will throw HIM Mnd et

V.; I pet in! M he 5 / w y | Be, 3 1 BK Y Koch I

FI FI -.8 ki in . eru sk Still ih y t y M / kh zh oy o de tia zh zh v zh ov oz A Her "y y anna nu Ron nn nyny -E t rutu ; nt i : Y i Port s i. sht p r Za YN m ia i y Ki - schi AS z i Ka 1 ory dinya V z Ne: i tr a Pane I sefay v Y Y x i i Z v u y y ki Iz t u ! / E i and 5 same sh and 5; and I

I N N KZ d i I t-e - t 18 o Z Se B h v sho sanei nen no pli r y oh v

X actions and the same kV

Fig. From

1 Visha t il liny vdi nin NHI svyadosh ia pi m akh oka zo Y PONNYN r DNA AK 33 A Uzh i 5 et pi - g. 5 "Fig, in

Ж хх ХЕ ХЕ Ох мк) х | all | as still nin nshne

ГИ ии 115-715" with ои І 1 and І і і І | Y Kk vi | | | | 1 « nia 11709202 1 x ' t

Pine cones 1 and 1 and 7 Ж SAME ЖЖ 5

Yes, yes, yes

Fig. 7

Kk she K n- -i- sr in 7 52 -52 fo F. 52 Ky

FIG. 8 FIG. 8 FIG. 10 FIG, 11 and Y- -- well shi in Uk il ni only SHY (X vm -e tol. -sh-

N

-52 and 52 x ! 52 | 52 - yours;

FIG. 12 FIG. 3 FIG. 14 FIG. 15 yav - U t Ka i what kA ni s - | Kk A. I! Y -- I x x mon nn KI vka; of "U, / y and Z ' Ann ! ; von I on oy has / I gg | Kin

FIG. 16 Fairies? Fig. ate

Computer layout 0. Gaponenko Signature Circulation 26 approx.

Ministry of Education and Science of Ukraine

State Department of Intellectual Property, str. Urytskogo, 45, Kyiv, MSP, 03680, Ukraine

SE "Ukrainian Institute of Industrial Property", str. Glazunova, 1, Kyiv - 42, 01601